CN112296611A - Processing technology of jet pipe shell of aerospace transmitter - Google Patents
Processing technology of jet pipe shell of aerospace transmitter Download PDFInfo
- Publication number
- CN112296611A CN112296611A CN202011279594.6A CN202011279594A CN112296611A CN 112296611 A CN112296611 A CN 112296611A CN 202011279594 A CN202011279594 A CN 202011279594A CN 112296611 A CN112296611 A CN 112296611A
- Authority
- CN
- China
- Prior art keywords
- welding
- weldment
- blank
- forging
- aerospace
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The scheme discloses a processing technology of a spray pipe shell of an aerospace transmitter, which comprises forging, heat treatment, rough machining and welding, wherein a forged blank weldment is subjected to heat preservation at 880-900 ℃ for 300min +/-10 min and then is subjected to air cooling; then, putting the workpiece into an electric furnace at 300-400 ℃ for heat preservation for 2 hours, and assembling the finished product weldment 1 and the finished product weldment 2 on a welding tool; the welding conditions during welding are welding current of 1000-1200A, arc voltage of 42-44V, welding speed of 25-28 m/h and current density of 28-42A/mm2The extension length of the welding wire is 40-50 mm, and the inclination angle between the welding wire and the workpiece is 6-8 degrees; heating the welded part in a box type resistance furnace to 890-910 ℃, preserving heat for 300min, then carrying out oil cooling and tempering: and (3) carrying out oil cooling after the temperature is 510-560 ℃ and the heat preservation is carried out for 120min, and then machining is carried out on a lathe according to the required specification to obtain the spray pipe shell. Compared with the prior art, the process reduces the material consumption and improves the processing efficiency.
Description
Technical Field
The invention belongs to the technical field of processing of a nozzle shell of an aerospace transmitter, and particularly relates to a processing technology of the nozzle shell of the aerospace transmitter.
Background
In the field of manufacturing of solid rocket engines, a thrust vector control technology is also called a thrust steering technology, and the missile maneuvering orbital transfer flight is controlled by controlling the jet flow direction of a nozzle of a rocket engine. The nozzle shell is a device used for thrust vector control. The structure of the nozzle shell is shown in fig. 3, 4 and 5, and comprises a finished product weldment 1 and a finished product weldment 2, wherein the finished product weldment 2 is funnel-shaped, the finished product weldment 1 is horn-shaped, and a wide mouth section of the finished product weldment 2 is connected with a narrow mouth end of the finished product weldment 1 in a welding mode.
The nozzle shell series part is made of 30CrMnSiA, the chemical components of the nozzle shell series part comprise C (0.28-0.35 percent of GJB1951 standard mass percentage, the following is the same), Si (0.90-1.20 percent), Mn (0.80-1.10 percent), Cr (0.80-1.10 percent) as main elements, S (less than or equal to 0.025 percent), P (less than or equal to 0.025 percent), Ni (less than or equal to 0.40 percent) and Cu (less than or equal to 0.025 percent) as residual elements. Normalizing and tempering (air cooling at 880-900 ℃, air cooling at 690-710 ℃ and HB 156-229) after heat treatment of the weldment, welding, removing stress, and delivering after flaw detection.
The section 25 (the section of 25 multiplied by 25 or phi 25) of the sample, oil quenching at 880-900 ℃, oil cooling at 500-560 ℃, and the mechanical properties of the sample meet the conditions that sigma b is more than or equal to 1080MPa, sigma s is more than or equal to 835MPa, delta 5 is more than or equal to 10%, psi is more than or equal to 45%, Akv is more than or equal to 39J, Akv is more than or equal to 49J/cm2, HB: 302 to 363.
The 30CrMnSiA material has higher strength and enough toughness after quenching and tempering, belongs to medium carbon quenched and tempered steel, and has higher hardenability, so the welding performance is poorer.
The prior art process route for processing the distribution shell is as follows: forging, heat treatment, rough machining, welding, and delivering after inspection. The existing process has the following defects: (1) directly heating by a steel ingot, forging into a cylinder body, and forging to the size shown in figure 1, wherein the material consumption 1950kg and the material utilization 203/1950 is 0.104 to 10.4 percent. (2) It took 68 hours (more than one week) to rough to delivery size after heat treatment. The existing spray pipe shell processing technology has the technical problems of low material utilization rate, long period and low efficiency.
Disclosure of Invention
The invention aims to provide a processing technology of a nozzle shell of an aerospace transmitter, and aims to solve the technical problems of high material consumption and low efficiency of the existing processing technology.
The processing technology of the jet pipe shell of the aerospace transmitter comprises the following steps:
step one, manufacturing a blank weldment 1:
(1) forging the blank weldment 1:
1) discharging, using
Long length of bar stock
2) Heating, namely heating to 1000-1200 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 1;
3) forging, namely placing the blank 1 into a selected existing forming die on a quick forging hydraulic press for upsetting, punching, reaming and shaping, and performing sand cooling after forging;
(2) forging the blank weldment 2:
1) discharging, using
Long length of bar stock
2) Heating, namely heating to 1000-1200 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 2;
3) forging, namely putting the blank 2 into a selected existing forming die on a quick forging hydraulic press for upsetting, punching blind holes, pressing a punch, reversely punching a core material, taking out the forming die for shaping, and performing sand cooling after forging;
step two, normalizing the blank weldment: keeping the temperature of the forged blank weldment 1 and blank weldment 2 at 880-900 ℃ for 300min +/-10 min, and then cooling in air;
step three, rough machining of blank weldment: rough machining is carried out on the blank weldment 1 and the blank weldment 2 after the second step according to the required sizes to obtain a finished product weldment 1 and a finished product weldment 2 respectively, then the finished product weldment 1 and the finished product weldment 2 are placed in an electric furnace at 300-400 ℃ for heat preservation for 2 hours, and the finished product weldment 1 and the finished product weldment 2 are assembled on a welding tool;
step four, welding: using a direct current automatic submerged arc welding machine, wherein the welding conditions are as follows: welding current is 1000-1200A, arc voltage is 42-44V, welding speed is 25-28 m/h, and current density is 28-42A/mm2The extension length of the welding wire is 40-50 mm, and the inclination angle between the welding wire and the workpiece is 6-8 degrees; under the welding condition, welding the wide mouth section of the finished weldment 2 and the narrow mouth end of the finished weldment 1 to obtain a weldment;
step five, post-welding stress removal treatment: heating the welded part in a box type resistance furnace to 890-910 ℃, preserving heat for 300min, then carrying out oil cooling and tempering: and (3) carrying out oil cooling after the temperature is 510-560 ℃ and the heat preservation is carried out for 120min, and then machining is carried out on a lathe according to the required specification to obtain the spray pipe shell.
The working principle and the beneficial technical effects of the scheme are as follows:
(1) and (3) adding machining allowance of 3-5 mm on the basis of the delivery size diagram, designing a finished weldment assembly diagram, effectively preventing welding deformation, and ensuring that the welding member meets the delivery size requirement after rough turning.
(2) The blank weldment is manufactured firstly, and raw materials are greatly saved according to the requirements of the designed finished product weldment through the existing tooling such as a forming die, a punch and the like.
(3) After-welding stress relief treatment is carried out under the set conditions, the blank weldment structure is stabilized, and the forging stress is eliminated; the selected technical parameters effectively ensure that the body and the weld joint of the finished weldment are uniform in structure, eliminate welding stress and meet the overall performance requirements of the finished weldment.
(4) Saving material and improving the utilization rate of the material. The weight of the processed spray pipe shell reaches the standard and reaches the delivery state, the weight of the processed spray pipe shell is 203kg, the processing consumed materials 1950kg of the forged straight barrel body are obtained, the material utilization rate is 10.4%, the consumed materials of the assembly is 735kg, the material utilization rate is 27.6%, the materials are saved by 1215kg, and the materials are saved by 62.3%.
(5) The whole manufacturing period of the scheme is about 78h, while the manufacturing period of the prior art is about 112h, so the scheme shortens the manufacturing period and improves the processing efficiency. In addition, from the technical route of the prior art and the technical route of the invention, the time required by the detection test and the time required by the packaging and transportation are consistent, the detection test is carried out on the body by sampling, and the mechanical property detection test is carried out after the sample is processed after quenching and tempering, so that the great change is avoided.
Further, covering the welding part with asbestos cloth during welding in the third step, and keeping the temperature. The heat preservation can prevent the welding seam from being cooled too fast to crack.
Further, after welding and before post-welding stress relief treatment, the welded part is cooled, the welded part is firstly polished or turned, and then liquid permeation inspection and ultrasonic inspection are sequentially carried out. Whether surface welding cracks exist or not is checked through liquid permeation, whether welding internal cracks exist or not is checked through ultrasonic waves, if welding cracks and internal cracks exist, timely remediation is carried out before post-welding stress relief treatment, and the condition that rework or abandonment caused by final inspection disqualification can be reduced.
Further, the temperature of the high-temperature electric furnace in the first step is heated to 1180 +/-10 ℃. 1180 +/-10 ℃ is the ideal heating temperature of 30CrMnSiA, the temperature above which the forging is easy to overheat, the temperature below which the metal resistance is large and the deformation is difficult, and the forging heat number is increased, thereby increasing the manufacturing cost.
Further, the load bearing of the fast forging hydraulic machine adopted in the forging in the step one is an 800T fast forging hydraulic machine. : the 800T quick forging hydraulic press belongs to static pressure forming equipment, the forging capability can meet the forming force required by a spray pipe shell, the forming force is not suitable when the forming force is too large or too small, and the nominal pressure of the equipment is 800 tons when the forming force is 800T.
Further, the temperature for heat preservation in the third step is 350 ℃.
Furthermore, when welding is carried out in the third step, the specification of the adopted welding wire is 6 multiplied by L, HJ431 is selected as a welding flux, a welding rod A507 is positioned,
the flux and the welding rod are dried and placed separately, the pile height is below 60mm, and the flux and the welding rod are placed in an insulation box for storage before use.
Further, the drying conditions of the flux and the welding rod are 200-350 ℃, and the heat preservation time is more than 1 h.
Drawings
FIG. 1 is a cross-sectional view in the axial plane of a nozzle shell according to the present invention;
FIG. 2 is a schematic structural view of a straight barrel (blank) of the nozzle shell according to the present invention;
FIG. 3 is a schematic structural view of a nozzle casing assembly weldment;
FIG. 4 is a schematic structural view of the finished weldment 1;
FIG. 5 is a schematic view of the structure of the finished weld 2;
FIG. 6 is a schematic structural view of a blank weldment 1;
FIG. 7 is a schematic structural view of a blank weldment 2;
FIG. 8 is a prior art roadmap;
FIG. 9 is a technical route diagram of the nozzle shell processing technique of the aerospace transmitter of the invention.
Detailed Description
The following is further detailed by way of specific embodiments:
the embodiment 1 is a nozzle shell processing technology of an aerospace transmitter, which comprises the following steps of forging, heat treatment, rough machining and welding:
step one, manufacturing a blank weldment 1:
(1) forging of blank weldment 1 welded as shown in fig. 6:
1) discharging, using
Long length of bar stock
The weight of the discharged material was 320 kg.
2) Heating, namely heating to 1000 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 1.
3) Forging, namely placing the blank 1 into a selected existing forming die on an 800T quick forging hydraulic press for upsetting, punching, reaming and shaping, and performing sand cooling after forging;
(2) forging of the blank weldment 2 as shown in fig. 7:
1) discharging, using
Long length of bar stock
The weight of the discharged material was 320 kg.
4) Heating, namely heating to 1000 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 2.
5) Forging, namely placing the blank 2 into a selected existing forming die on an 800T quick forging hydraulic press, upsetting, punching blind holes, pressing by a punch, reversely punching core materials, taking out the forming die for shaping, and performing sand cooling after forging;
step two, normalizing the blank weldment: keeping the temperature of the forged blank weldment 1 and blank weldment 2 at 900 ℃ for 300min +/-10 min, and then cooling in air;
step three, rough machining of blank weldment: rough machining is carried out on the blank weldment 1 and the blank weldment 2 after the second step according to the sizes shown in the figures 4 and 5 to respectively obtain a finished product weldment 1 and a finished product weldment 2, asbestos cloth is covered on a welding part for heat preservation during welding, then the finished product weldment 1 and the finished product weldment 2 are placed in an electric furnace at 400 ℃ for heat preservation for 2 hours, and the finished product weldment 1 and the finished product weldment 2 are assembled on a welding tool;
step four, welding:
(1) preparation before welding: the specification of the adopted welding wire is 6 multiplied by L, HJ431 is selected as a welding flux, a welding rod A507 is positioned,
drying the flux and the welding rod under the drying condition of 200 ℃, preserving heat for more than 1h, separately placing the flux and the welding rod, piling the flux and the welding rod at a height of less than 60mm, and storing the flux and the welding rod in a heat preservation box for later use before use;
(2) using an MZ-1250 direct current automatic submerged arc welding machine, wherein the welding conditions are as follows: welding current is 1000-1200A, arc voltage is 42-44V, welding speed is 25-28 m/h, and current density is 28-42A/mm2The extension length of the welding wire is 40-50 mm, and the inclination angle of the welding wire and the workpiece is 6-8 degrees; under the welding condition, welding the wide mouth section of the finished weldment 2 and the narrow mouth end of the finished weldment 1 to obtain a welded part; cooling the welded partsFirstly, polishing or turning a welding part, then carrying out ultrasonic inspection to determine whether surface welding cracks exist in the liquid, and then carrying out ultrasonic inspection to determine whether internal cracks exist in the welding; if flaw detection finds that a certain part has a crack, the part is polished (superficial surface) or machined (middle part) to remove the crack part, liquid permeation detection is carried out until the crack is completely removed, then local repair welding is carried out, and then the quality of the welding part is detected according to the mode;
in the welding operation, the welding conditions commonly used are: welding current 1050A, arc voltage 43V, welding speed 26m/h (i.e. 6.5 mm-7.5 mm per second), current density 30A/mm2The extension length of the welding wire is 50mm, and the inclination angle of the welding wire and the workpiece is 7 degrees; actual welding conditions are all within the above range;
step five, post-welding stress removal treatment: heating the welded part in a box type resistance furnace to 890-910 ℃, preserving heat for 300min, then carrying out oil cooling and tempering: and (3) carrying out oil cooling after the temperature is 510-560 ℃ and the heat preservation is carried out for 120min, and then machining is carried out on a lathe according to the required specification to obtain the spray pipe shell, as shown in figure 2.
Example 2: the differences from example 1 are: in the first step, the temperature of a high-temperature electric furnace is heated to 1180 ℃; in the second step, the temperature for heat preservation is 890 ℃; in the third step, the temperature for heat preservation is 350 ℃; the drying conditions of the flux and the welding rod were 300 ℃.
Example 3, the difference from example 1 is: in the first step, the temperature of a high-temperature electric furnace is heated to 1200 ℃; in the second step, the temperature for heat preservation is 880 ℃; in the third step, the temperature for heat preservation is 300 ℃; the drying conditions for the flux and the electrode were 350 ℃.
The invention discloses a processing technique of a spray pipe shell, which comprises the following working procedures of forging a blank weldment, normalizing the blank weldment, roughly processing the blank weldment, welding a finished product weldment, normalizing and tempering and the like.
And forging the first part of blank weldment, and forging the assembly blank by using the existing forming die and punch in a forging workshop.
And normalizing the blank weldment of the second part to eliminate forging stress and stabilize a forging structure.
And (3) rough machining of blank weldment of the third part, namely adding 3-5 mm of rough machining on the basis of delivery size.
And welding the fourth part finished weldment by using a special tool.
Normalizing and tempering the fifth part after welding to eliminate welding stress and stabilize the structure; and finally, roughly machining according to delivery size requirements (namely machining on a lathe according to the required specification to obtain the nozzle shell).
Due to the adoption of the scheme of the embodiment, the welding process technology of the spray pipe shell comprises the following steps:
(1) saving material and improving the utilization rate of the material.
As shown in FIG. 1, the weight of the tube shell obtained by the process of the present invention is 203kg in the delivery state, the material consumption rate of 1950kg in the process of forging the tube shell into a straight cylinder is 10.4%, the material consumption rate of the assembly is 735kg, the material consumption rate when the tube shell reaches the delivery state is 27.6%, 1215kg of material is saved, and the material saving rate is improved by 62.3%.
The method comprises the following steps: the forged straight barrel is shown in fig. 2, and the assembly blank is shown in fig. 6 and 7.
In fig. 2, 1950kg of blank weldment material (including blank weldment weight + blank weldment unevenness + fire loss + core material, the same below) is consumed (i.e. the blanking weight is 1950kg, the same below), and the weight is 203kg in the delivery state, and 203/1950 is 0.1041 is 10.4% (i.e. the material utilization rate of the forged straight cylinder). The assembly refers to a blank weldment 1 shown in figure 6 and a blank weldment 2 shown in figure 7, and the blank weldment 1 and the blank weldment 2 are assembled and welded into the part shown in figure 1 after being processed into parts. The blank welding member 1 consumes 320kg of blank materials, the blank welding member 2 consumes 415kg of blank materials, and the total amount is 735 kg.
The material utilization rate 203/735 is 0.27619-27.6%, the material saving 1950 and 735-1245 (kg), and the material saving 1245/1950 is 0.623-62.3% when the tube housing is delivered.
(2) Shortening the manufacturing cycle
From the prior art route and the technical route of the invention, the time required by the detection test and the package transportation is consistent, the detection test is carried out on the body in the two methods, the mechanical property detection test is carried out after the sample is processed after quenching and tempering, no big change is caused, and the comparison result is shown in table 1:
table 1: room temperature mechanical property parameters of the invention and the prior art
For this purpose, comparative analyses were carried out only on the forging to roughing which affected the production cycle.
1) The time required for the prior art route is shown in figure 8.
2) The technical route of the invention is shown in figure 9.
3) Manufacturing cycle analysis
In view of the time required by the prior art route and the present invention route, the prior art manufacturing cycle 112h (14 days), the present invention route manufacturing cycle 78h (9.75 days) can be completed at least 4 days in advance.
Claims (8)
1. The processing technology of the jet pipe shell of the aerospace transmitter is characterized by comprising the following steps of:
step one, manufacturing a blank weldment 1:
(1) forging the blank weldment 1:
1) discharging, using
Long length of bar stock
2) Heating, namely heating to 1000-1200 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 1;
3) forging, namely placing the blank 1 into a selected existing forming die on a quick forging hydraulic press for upsetting, punching, reaming and shaping, and performing sand cooling after forging;
(2) forging the blank weldment 2:
1) discharging, using
Long length of bar stock
2) Heating, namely heating to 1000-1200 ℃ in a 120KW high-temperature electric furnace, and preserving heat for 150min to obtain a blank 2;
3) forging, namely putting the blank 2 into a selected existing forming die on a quick forging hydraulic press for upsetting, punching blind holes, pressing a punch, reversely punching a core material, taking out the forming die for shaping, and performing sand cooling after forging;
step two, normalizing the blank weldment: keeping the temperature of the forged blank weldment 1 and blank weldment 2 at 880-900 ℃ for 300min +/-10 min, and then cooling in air;
step three, rough machining of blank weldment: rough machining is carried out on the blank weldment 1 and the blank weldment 2 after the second step according to the required sizes to respectively obtain a finished product weldment 1 and a finished product weldment 2, then the finished product weldment 1 and the finished product weldment 2 are placed in an electric furnace at 300-400 ℃ for heat preservation for 2 hours, and the finished product weldment 1 and the finished product weldment 2 are assembled on a welding tool;
step four, welding: using a direct current automatic submerged arc welding machine, wherein the welding conditions are as follows: welding current is 1000-1200A, arc voltage is 42-44V, welding speed is 25-28 m/h, and current density is 28-42A/mm2The extension length of the welding wire is 40-50 mm, and the inclination angle between the welding wire and the workpiece is 6-8 degrees; under the welding condition, welding the wide mouth section of the finished weldment 2 and the narrow mouth end of the finished weldment 1 to obtain a weldment;
step five, post-welding stress removal treatment: heating the welded part in a box type resistance furnace to 890-910 ℃, preserving heat for 300min, then carrying out oil cooling and tempering: and (3) carrying out oil cooling after the temperature is 510-560 ℃ and the heat preservation is carried out for 120min, and then machining is carried out on a lathe according to the required specification to obtain the spray pipe shell.
2. The aerospace emitter nozzle casing machining process of claim 1, wherein: and step three, covering the welding part with asbestos cloth during welding, and keeping the temperature.
3. The aerospace emitter nozzle casing machining process of claim 2, wherein: after welding and before stress relief treatment after welding, the welded part is cooled, the welded part is firstly polished or lathed, and then liquid permeation inspection and ultrasonic inspection are sequentially carried out.
4. A process for machining a nozzle shell for an aerospace launcher according to any one of claims 1 to 3, wherein: and heating the medium-high temperature electric furnace to 1180 +/-10 ℃ in the first step.
5. The aerospace emitter nozzle casing machining process of claim 4, wherein: in the first step, a fast forging hydraulic press with the load bearing of 800T is adopted for forging.
6. The aerospace emitter nozzle casing machining process of claim 5, wherein: the temperature for heat preservation in the third step is 350 ℃.
7. The aerospace emitter nozzle shell machining process according to any one of claims 1-3, 5, and 6, wherein: when welding is carried out in the third step, the specification of the adopted welding wire is 6 multiplied by L, HJ431 is selected as a welding flux, a welding rod A507 is positioned,
the flux and the welding rod are dried and placed separately, the pile height is below 60mm, and the flux and the welding rod are placed in an insulation box for storage before use.
8. The aerospace emitter nozzle casing machining process of claim 7, wherein: and the drying conditions of the flux and the welding rod are 200-350 ℃, and the heat preservation is carried out for more than 1 h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011279594.6A CN112296611B (en) | 2020-11-16 | 2020-11-16 | Processing technology of jet pipe shell of aerospace transmitter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011279594.6A CN112296611B (en) | 2020-11-16 | 2020-11-16 | Processing technology of jet pipe shell of aerospace transmitter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112296611A true CN112296611A (en) | 2021-02-02 |
| CN112296611B CN112296611B (en) | 2022-06-10 |
Family
ID=74334597
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011279594.6A Active CN112296611B (en) | 2020-11-16 | 2020-11-16 | Processing technology of jet pipe shell of aerospace transmitter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112296611B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013455A (en) * | 2022-05-30 | 2022-09-06 | 上海裴椒汽车部件制造有限公司 | Brake oil pipe joint and forming process thereof |
| CN116043129A (en) * | 2022-11-25 | 2023-05-02 | 重庆钢铁股份有限公司 | 30CrMnSiA structural alloy steel plate for aviation and manufacturing method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1005949A1 (en) * | 1998-11-30 | 2000-06-07 | United Technologies Corporation | Method of forming a rocket thrust chamber |
| CN102729007A (en) * | 2012-06-25 | 2012-10-17 | 湖北三江航天江北机械工程有限公司 | Method for producing bearing ball socket swinging spray pipe |
| CN110883540A (en) * | 2019-11-27 | 2020-03-17 | 西安长峰机电研究所 | Welding assembly process for thin-wall spray pipe shell of engine |
-
2020
- 2020-11-16 CN CN202011279594.6A patent/CN112296611B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1005949A1 (en) * | 1998-11-30 | 2000-06-07 | United Technologies Corporation | Method of forming a rocket thrust chamber |
| CN102729007A (en) * | 2012-06-25 | 2012-10-17 | 湖北三江航天江北机械工程有限公司 | Method for producing bearing ball socket swinging spray pipe |
| CN110883540A (en) * | 2019-11-27 | 2020-03-17 | 西安长峰机电研究所 | Welding assembly process for thin-wall spray pipe shell of engine |
Non-Patent Citations (1)
| Title |
|---|
| 张鹏等: "固体火箭发动机用D6AC钢喷管壳体的加工工艺研究", 《航天制造技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013455A (en) * | 2022-05-30 | 2022-09-06 | 上海裴椒汽车部件制造有限公司 | Brake oil pipe joint and forming process thereof |
| CN115013455B (en) * | 2022-05-30 | 2024-05-03 | 上海裴椒汽车部件制造有限公司 | Brake oil pipe joint and forming process thereof |
| CN116043129A (en) * | 2022-11-25 | 2023-05-02 | 重庆钢铁股份有限公司 | 30CrMnSiA structural alloy steel plate for aviation and manufacturing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112296611B (en) | 2022-06-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112296611B (en) | Processing technology of jet pipe shell of aerospace transmitter | |
| CN103111808B (en) | A kind of nickel base superalloy GH4169 hexagon socket head cap screw processing technologys | |
| EP3682982B1 (en) | Manufacturing process for large annular forged piece | |
| CN101722262B (en) | New method for producing medium and large caliber alloy steel seamless pipe by utilizing radial forging technology | |
| CN109834396A (en) | Composite tooling and thrust chamber welding procedure for thrust chamber welding | |
| CN113510216B (en) | Forging forming method for niobium-tungsten alloy ring-shaped piece | |
| CN111531097B (en) | Forging method for eliminating wall thickness unevenness defect of cylinder type forging | |
| EP3683007A1 (en) | Profiled metal construction forming method | |
| CN108188659A (en) | A kind of manufacturing process of steel billet | |
| CN106964950B (en) | Processing technology of open type cavity forging die working face | |
| CN109352288A (en) | A kind of automobile gimbal fork single piece cold extrusion compression moulding technique | |
| CN105328414B (en) | A kind of forming method of automobile section fork | |
| CN110614338A (en) | Forging method of GH4169 alloy steel round bar | |
| CN112718910A (en) | Manufacturing method of large-caliber TC4 titanium alloy thick-wall pipe | |
| CN114055092A (en) | Method for manufacturing air-hole ultrahigh-pressure pipe fitting by high-nickel alloy structural steel | |
| CN108188658B (en) | Composite roller preparation process | |
| CN111167984B (en) | Forging method for forging sector plate by using arc anvil | |
| CN107186444A (en) | A kind of hubbed flange processing technology | |
| CN111151693A (en) | Forming method for forging fillet square steel by precision forging machine | |
| CN1265913C (en) | Retaining ring steel hot forging technology for generator | |
| CN110586825B (en) | Free forging method of step inner hole cylinder forging | |
| KR20140006186A (en) | Holding part forming type upsetting dies for a heavy metal forging process and the heavy metal forging process by it | |
| CN110625334A (en) | Machining method for reducing deformation of slender thin-wall rocket combustion chamber shell | |
| CN110605542B (en) | Titanium alloy wheel disc for gas turbine and drum destressing process method | |
| CN112517817A (en) | Free forging process of thin-wall special-shaped step barrel part |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |